Extendable Solar Array Boom for Passive Attitude Stabilization
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Solution Overview
Problem
Conventional solar arrays for spacecraft are limited in providing efficient, lightweight, and robust solar power while also achieving passive attitude stabilization through gravity gradient forces, which is crucial for maintaining accurate satellite orientation and power generation.
Innovation Solution
The development of extendable solar arrays that include a solar array apparatus with extendable booms and deployment mechanisms, allowing the solar arrays to transition from a stowed to a deployed configuration, distributing mass for passive attitude stabilization and increasing power generation capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional solar arrays are used for spacecraft, then solar power generation is provided, but the arrays cannot achieve passive attitude stabilization through gravity gradient forces
Solution Approach 1:
The solar array system transitions from a static configuration to a dynamic deployable structure. The solar arrays are stored in a compact configuration during launch and then deployed to an extended operational configuration in orbit. This dynamic transformation enables the system to achieve passive attitude stabilization through gravity gradient forces while maintaining the ability to provide solar power generation, thereby resolving the contradiction between reliability and adaptability.
2Weight of moving object
If solar arrays are made lightweight for spacecraft, then power-to-weight ratio improves, but structural robustness and stability may be compromised
Solution Approach 1:
The solar arrays utilize thin-film or flexible photovoltaic structures that provide high power generation capability with minimal mass. These flexible solar array structures are designed to be lightweight while maintaining sufficient structural integrity when deployed, resolving the contradiction between weight reduction and structural robustness required for spacecraft applications.
Solution Approach 2:
The deployable nature of the solar arrays allows them to achieve full structural strength only when deployed to their operational configuration in orbit, rather than requiring constant heavy reinforcement throughout launch and storage. This dynamic approach enables lightweight construction that gains structural robustness when needed for power generation and attitude stabilization.
3Power
If solar arrays are extended to increase power generation, then energy collection improves, but device complexity and deployment mechanisms increase
Solution Approach 1:
The solar array system is divided into multiple deployable panels or segments that can be independently stored and deployed. This segmentation allows the solar arrays to achieve extended surface area for high power generation while using simpler, modular deployment mechanisms for each segment, rather than requiring a single complex mechanism to deploy a large monolithic structure.
Solution Approach 2:
The solar arrays employ deployable structures that transition from compact storage to extended operational configurations. This dynamic approach enables the system to achieve large surface area for high power generation only when needed in orbit, while maintaining a compact, low-complexity storage configuration during launch, thereby resolving the contradiction between power generation capability and device complexity.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The extendable solar arrays provide a simple, lightweight, high-power, and robust means of solar power generation while achieving passive attitude stabilization, enhancing power levels and attitude control for spacecraft, allowing for efficient energy collection and stable satellite orientation.
Implementation Method 1
The at least one solar array may extend between the first portion and the second portion to collect incident radiation
Implementation Method 2
The extendable solar arrays may also distribute the mass of the spacecraft to provide passive attitude stabilization from gravity gradient forces
Data Source
AI summary
A spacecraft system may include a storage portion (e.g., a first portion and a second portion) and a solar array apparatus that may be configurable in at least a stowed configuration and a deployed configuration. The solar array apparatus may include at least one solar array to collect incident radiation when the solar array apparatus is in the deployed configuration. In one or more embodiments, the at least one solar array may extend away from the storage portion. In one or more embodiments, the at least one solar array may extend between the first portion and the second portion. The solar array apparatus may also include an extendable boom operable to extend the at least one solar array apparatus from the stowed configuration to the deployed configuration.